Title

Rotational maneuver of nonlinear uncertain elastic spacecraft

Document Type

Article

Publication Date

3-1988

Publication Title

IEEE Transactions on Aerospace and Electronic Systems

Volume

24

First page number:

114

Last page number:

123

Abstract

The question of attitude control and elastic mode stabilization of a spacecraft (orbiter) with beam-tip-mass-type payloads is considered. A three-axis moment control law is derived to control the attitude of the spacecraft. The derivation of the control moments acting on the spacecraft does not require any information on the system dynamics. The control law includes a reference model and a dynamic compensator in the feedback path. For damping out the elastic motion excited by the slewing maneuver, an elastic mode stabilizer is designed. The stabilization is achieved by modal velocity feedback using force and torque actuators located at the payload end of the elastic beam. Collocated actuators and sensors provide robust stabilization. Simulation results are presented to show that rotational maneuvers and vibration stabilization can be accomplished in the closed-loop systems despite the presence of model uncertainty and disturbance torque in the system.

Keywords

Actuators; Attitude control; Control systems; Damping; Force feedback; Force sensors; Payloads; Robustness; Space vehicles; Torque

Disciplines

Aeronautical Vehicles | Aerospace Engineering | Electrical and Computer Engineering | Multi-Vehicle Systems and Air Traffic Control | Navigation, Guidance, Control and Dynamics | Power and Energy | Propulsion and Power | Signal Processing | Space Vehicles | Structures and Materials

Language

English

Permissions

Use Find in Your Library, contact the author, or interlibrary loan to garner a copy of the item. Publisher policy does not allow archiving the final published version. If a post-print (author's peer-reviewed manuscript) is allowed and available, or publisher policy changes, the item will be deposited.

Identifier

DOI: http://dx.doi.org/10.1109/7.1044

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